WIT Press

Thermomechanical Optimisation Of Fatigue Strength For Aircraft Engine Parts

Price

Free (open access)

Paper DOI

10.2495/SURF970341

Volume

17

Pages

9

Published

1997

Size

706 kb

Author(s)

P.D. Zhemanyuk, I.E. Kovalev, V.G. Mikhailutsa, S. A. Voitenko, F.P. Banas, A.P. Petrov & A.E. Kovalev

Abstract

Thermomechanical optimisation of fatigue strength for aircraft engine parts P. D. Zhemanyuk*, I. E. Kovalev\ V. G. Mikhailutsa*, S. A. Voitenko*, F. P. Banas\ A. P. Petrov\ A. E. Kovalev^ Moscow a^e^v^mA7-r^c^^ [/M/ Moscow, Russia The manufacturing process of compressor blades from heat-resistant double-phase titaniun alloy BT8M1 (Ti-5Al-4Mo-lSn-lZr) for Motor-Sich JSC turbo-shaft engine has been studied. The objective of study was definition of the manufacturing factors affe- cting the blades altering of resistance to fatigue and definition of critical points of the manufacturing process. The above mentioned blades are subjected under manufacture to three steps of cold plastic deformation with intermediate heat treatments in the following sequence: 1) primary forge-rolling, 2) high temperature annealing at 930° C, 3) the second forge-rolling, 4) low temperature annealing at 590° C, 5) surface hardening. Modelling of blade

Keywords